摘要
长焦距空间遥感器次镜热控实施难度大、发射动态响应大,因此,必须具有较宽的温度适应范围和较高的动态刚度。文中阐明了次镜支撑方式的基本原则,并从材料选择、消热设计等角度出发,设计了一种柔性支撑结构;对该支撑的3个柔性环节进行了灵敏度分析,得到了各自对次镜面形精度影响的程度;通过优化设计确定了该支撑的尺寸参数,并对次镜组件进行了有限元分析;最后进行了组件的动力学试验和热试验。分析表明,15℃均匀温升工况下,次镜面形RMS为9.8 nm,组件一阶固有频率为153 Hz;试验表明,15℃均匀温升工况下,次镜面形精度满足成像要求,组件一阶固有频率为150 Hz,各项静态指标满足设计要求。
In space telescopes with long focal length, the secondary mirror should be designed with high dynamic stiffness and an adaptability of wide range temperature because its thermal control is difficult to be implemented in orbit and its dynamic response is very large during launch. Firstly, the design principle of secondary mirror＇ s support was specified, and a flexible support was designed from the views of material selection and thermal design. Secondly, three flexible links were analyzed by sensitivity analysis and their effects on surface figure accuracy were found, then the final sizes of the flexible support were obtained. Subsequently, an elaborate finite element analysis was made. Finally, dynamic and thermal test were made. Analysis shows that the secondary mirror＇s RMS is 9.8 nm under 15℃ uniform temperature rise, the first order natural frequency is 150 Hz. Tests show that the RMS is 6.9 nm, the first order resonance frequency is 153 Hz. Analysis and tests verify that the support meets all design indexes.
出处
《红外与激光工程》
EI
CSCD
北大核心
2011年第9期1724-1729,共6页
Infrared and Laser Engineering
基金
国家863计划(2009AA7020107)
关键词
空间相机
离轴TMA
反射镜
柔性支撑
有限元分析
space camera
off-axis three mirror anastigmatic
reflecting mirror
flexible support
finite element analysis
